Abstract: An example compressor includes a casing having a main portion and an outer skirt collectively defining an annular plenum, an outlet guide vane coupled to the main portion, an actuator mounted outside the outer skirt, and a linkage coupled to the actuator and the outlet guide vane through the annular plenum.

Abstract: An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.

Abstract: An engine includes a stripping gas source, a combustion section, and a fuel oxygen conversion unit positioned upstream of the combustion section, the fuel oxygen conversion unit defining a stripping gas flowpath in airflow communication with the stripping gas source. The fuel oxygen conversion unit includes a contactor defining a fuel inlet, a gas inlet in airflow communication with the stripping gas flowpath, and a fuel gas mixture outlet; and a fuel gas separator defining a fuel gas mixture inlet for receiving a fuel gas mixture from the contactor, a liquid fuel outlet, and a stripping gas outlet; wherein the stripping gas flowpath receives substantially all of a stripping gas flow therethrough from the stripping gas source and provides the stripping gas flow to the contactor.

Abstract: A fuel delivery system for a gas turbine engine including a fuel oxygen reduction unit is provided. The fuel oxygen reduction unit defines a liquid fuel flowpath and a stripping gas flowpath and is configured to transfer an oxygen content of a fuel flow through the liquid fuel flowpath to a stripping gas flow through the stripping gas flowpath. The fuel oxygen reduction unit includes an impeller in airflow communication with the stripping gas flowpath for circulating the stripping gas flow through the stripping gas flowpath; and a turbine coupled to the impeller.

Abstract: A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.

Abstract: An example compressor includes a casing having a main portion and an outer skirt collectively defining an annular plenum, an outlet guide vane coupled to the main portion, an actuator mounted outside the outer skirt, and a linkage coupled to the actuator and the outlet guide vane through the annular plenum.

Abstract: A bearing assembly including a body defining an outer surface, an inner surface, and an aft surface is generally provided. A first inlet opening is defined through the outer surface in fluid communication with a first internal passage defined by a first internal wall. The first internal passage is in fluid communication with a first outlet opening defined through the inner surface. A second inlet opening is defined through the inner surface in fluid communication with a second internal passage defined by a second internal wall. The second internal passage is in fluid communication with a second outlet opening defined through the aft surface.

Abstract: A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.

Abstract: A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.

Abstract: A compressor apparatus includes: an upstream portion comprising an axial-flow compressor; a downstream portion comprising a centrifugal-flow compressor; and a row of variable-stagger-angle outlet guide vanes disposed between the upstream and downstream portions.

Abstract: An engine includes a stripping gas source, a combustion section, and a fuel oxygen conversion unit positioned upstream of the combustion section, the fuel oxygen conversion unit defining a stripping gas flowpath in airflow communication with the stripping gas source. The fuel oxygen conversion unit includes a contactor defining a fuel inlet, a gas inlet in airflow communication with the stripping gas flowpath, and a fuel gas mixture outlet; and a fuel gas separator defining a fuel gas mixture inlet for receiving a fuel gas mixture from the contactor, a liquid fuel outlet, and a stripping gas outlet; wherein the stripping gas flowpath receives substantially all of a stripping gas flow therethrough from the stripping gas source and provides the stripping gas flow to the contactor.

Abstract: A bearing assembly including a body defining an outer surface, an inner surface, and an aft surface is generally provided. A first inlet opening is defined through the outer surface in fluid communication with a first internal passage defined by a first internal wall. The first internal passage is in fluid communication with a first outlet opening defined through the inner surface. A second inlet opening is defined through the inner surface in fluid communication with a second internal passage defined by a second internal wall. The second internal passage is in fluid communication with a second outlet opening defined through the aft surface.

Abstract: A diffuser for a centrifugal compressor including an annular diffuser housing having a plurality of diffuser flow passages therethrough the housing. Each passage including a throat portion and a diffusing section with upstream and downstream diffusing portions. A diffusing passage centerline includes a linear portion extending downstream through the throat portion and the upstream diffusing portion and a curved portion of the diffusing passage centerline extending downstream from the centerline linear portion through the downstream diffusing portion. The diffuser flow passages may have an equivalent cone angle varying non-linearly or more particularly curvilinearly downstream along curved portion. The downstream diffusing portion may be flared.

Abstract: A centrifugal compressor apparatus includes: an impeller mounted for rotation about a central longitudinal axis, the impeller including an impeller disk carrying an array of impeller blades around its periphery; a diffuser disposed downstream of the impeller, configured to diffuse and turn airflow discharged from the impeller; an extraction scoop disposed in fluid communication with the impeller and with a plenum disposed adjacent the impeller, and a dirt collector disposed in fluid communication with the plenum and configured to trap dirt therein.

Abstract: An apparatus and method relating to a turbine engine with an annular frame about a centerline defining an axial direction, the annular frame formed from an inner frame wall and an outer frame wall disposed around and radially spaced from the inner frame wall to define an annular airflow passage between the inner and outer frame walls. The annular frame further includes at least two struts each extending between a root at the inner frame wall and a tip at the outer frame wall to define a span-wise direction.

Abstract: An engine component for a turbine engine includes a particle collector having a substrate configured to retain at least some particles from a particle-laden stream passing through a portion of the engine. A fluid bypass around the substrate of the collector enables the particle-laden stream to bypass the substrate if the substrate is filled with particles.

Abstract: A diffuser for a centrifugal compressor including an annular diffuser housing having a plurality of diffuser flow passages therethrough the housing. Each passage including a throat portion and a diffusing section with upstream and downstream diffusing portions. A diffusing passage centerline includes a linear portion extending downstream through the throat portion and the upstream diffusing portion and a curved portion of the diffusing passage centerline extending downstream from the centerline linear portion through the downstream diffusing portion. The diffuser flow passages may have an equivalent cone angle varying non-linearly or more particularly curvilinearly downstream along curved portion. The downstream diffusing portion may be flared.

Abstract: A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.

Abstract: Systems and methods for integrated power and thermal management in a turbine-powered aircraft are provided. The systems may include rotationally-independent first and second auxiliary power unit shafts, a power turbine, a first compressor, a second compressor, a cooling turbine, and an electrical motor-generator. The power turbine may be rotatably disposed on the first auxiliary power unit shaft. The first compressor may be rotatably disposed on the first auxiliary power unit shaft. The second compressor may be rotatably disposed on the second auxiliary power unit shaft. The cooling turbine may be rotatably disposed on the second auxiliary power unit shaft. The electrical motor-generator may disposed on the first auxiliary power unit shaft to alternatively supply a motive force input to the first auxiliary power unit shaft and an electrical power output to the aircraft.

Abstract: A separator assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle separator for separating the fluid stream into a reduced-particle stream and a particle-laden stream, and emitting the particle-laden stream through a scavenge outlet. Another particle remover is fluidly coupled to the scavenge outlet to remove more particles from the air stream.